Dassault Falcon 50
Development of the new Falcon 50 began in May 1974 with some components modelled after those of the earlier Falcon 20, including the front and centre fuselage sections. The Falcon 50 makes use of double-slotted trailing-edge flaps advanced high-lift devices. Powered by three Garrett AiResearch TFE 731-3 turbofan engines, each flat-rated at 3,700 lbs. s.t. (1680 kgp) for takeoff. Two are mounted separately in pods on each side of the rear fuselage; the third is located in the tailcone with its intake just forward of the base of the vertical stabilizer. In order to make room for this third engine, the fuselage was lengthened and the fin was enlarged over that of the Falcon 20.
Dassault-Breguet flew the prototype (F-WAMD) on 7 November 1976 and, with fully-developed supercritical wing, on 6 May 1977. The second prototype made its first flight in February 1978. The airplane's gross weight was increased from 37,480 to 38,800 pounds, including an additional 400 pounds of fuel; and the range went from 3,040 to 3,500 nm at Mach 0.73.
The French (27 February 1979) and U.S. Governments certificated the Dassault-Breguet Falcon 50 three-engine business jet in 1979. The first production Falcon 50 flew on 7 March 1979.
The three-engine Falcon 50 was designed for long range jet transport (originally 3,500 nm), and Dassault continued to refine that theme.
Dassault Falcon 50EX P4-JET
In 1995 Dassault announced the longer range Falcon 50EX featuring TFE73140 engines which added another 400 nm to the airliner’s range. The first models came off the production line in 1996.
The Falcon 50EX has more fuel efficient engines and greater range as well as a full EFIS cockpit display.
Falcon 50 YV1496
Engines: 3 x Garrett TFE 731-3, 3700 lbs thrust.
Length: 60.8 ft. / 18.52 m
Height: 22.8 ft. / 6.97 m
Wingspan: 61.8 ft.
Wing area: 504 sq.ft. / 46.8 sq.m
Wing aspect ratio: 7.6.
Maximum ramp weight: 38,800 lbs.
Maximum takeoff weight: 38,800 lbs.
Standard empty weight: 20,240 lbs.
Maximum useful load: 18,560 lbs.
Zero-fuel weight: 24,225 lbs.
Maximum landing weight: 35,715 lbs.
Wing loading: 77 lbs/sq.ft.
Power loading: 3.5 lbs/lb.
Maximum usable fuel: 15,520 lbs.
Best rate of climb: 3526 fpm.
Certificated ceiling: 45,000 ft.
Max pressurisation differential: 8.8 psi.
8000 ft cabin alt @: 45,000 ft.
Maximum engine out rate of climb: 2125 fpm @ 210 kts.
Engine out climb gradient: 610 ft/nm.
Engine out ceiling: 25,200 ft.
Maximum speed: 482 kts.
Normal cruise @ 39,000ft: 447 kts.
Fuel flow @ normal cruise: 1856 pph.
Stalling speed clean: 128 kts.
Stalling speed gear/flaps down: 95 kts.
Turbulent-air penetration speed: 280 kts.
Crew : 2
Payload : 10 Pax
Engines: 3 x Allied Signal TFE73140 turbofans, 3,700-lb.
Gross weight: 39,700 lb
Empty weight: 21,270 lb
Max cruise: 475 kts.
Ceiling: 45,000 ft
Takeoff run: 5,415 ft
Landing roll: 3,280 ft